Numerical Modelling and Analysis of the Burning Transient in a Solid-Propellant Micro-Thruster

摘要

This work investigates an architecture of arrayed micro-thrusters of submillimeter size for spacecraft propulsion. Each single thruster comprises a setup of micro-channels arranged around the solid-propellant reservoir, hence initial heating of both sides of its wall by the hot gas takes place in the transient Simulation of the unsteady response of the gas and wafer during the grain burning has been conducted under a multiphysics-based approach that fully couples the parts involved and focuses on the early phase of the transient Preliminary results suggest the beneficial role played by the thermal management provided by the micro-channels, that mitigates the heat loss across the wall Thus, miniaturization of the propellant reservoir within the submillimeter range is favoured due to the sustainment of higher temperatures ahead of the burning front, by the inner wall, Simulated firings show encouraging performance.